AH 94-145 (ah94145-il)
AH 94-145 - Althaus AH 94-145 airfoil
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(ah94145-il) AH 94-145 Althaus AH 94-145 airfoil Max thickness 14.6% at 38.9% chord. Max camber 5.6% at 44.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AH 94-145 1.00020 -0.00161 0.99043 0.00065 0.97609 0.00427 0.95715 0.00921 0.93617 0.01477 0.91469 0.02055 0.89312 0.02641 0.87154 0.03231 0.84996 0.03824 0.82838 0.04419 0.80681 0.05014 0.78524 0.05610 0.76367 0.06207 0.74209 0.06803 0.72058 0.07398 0.69922 0.07986 0.67810 0.08563 0.65730 0.09122 0.63695 0.09654 0.61707 0.10151 0.59763 0.10606 0.57854 0.11018 0.55967 0.11384 0.54089 0.11704 0.52210 0.11981 0.50324 0.12214 0.48429 0.12404 0.46525 0.12553 0.44616 0.12658 0.42704 0.12722 0.40789 0.12742 0.38868 0.12720 0.36939 0.12657 0.35001 0.12553 0.33058 0.12410 0.31113 0.12228 0.29170 0.12008 0.27233 0.11751 0.25307 0.11457 0.23393 0.11126 0.21496 0.10757 0.19621 0.10353 0.17773 0.09911 0.15956 0.09433 0.14177 0.08917 0.12444 0.08366 0.10769 0.07778 0.09162 0.07157 0.07638 0.06506 0.06220 0.05831 0.04931 0.05144 0.03799 0.04460 0.02846 0.03803 0.02080 0.03198 0.01489 0.02657 0.01041 0.02180 0.00707 0.01758 0.00458 0.01383 0.00276 0.01046 0.00147 0.00741 0.00061 0.00462 0.00013 0.00203 0.00000 -0.00039 0.00025 -0.00278 0.00097 -0.00517 0.00221 -0.00746 0.00399 -0.00958 0.00632 -0.01150 0.00921 -0.01324 0.01273 -0.01487 0.01707 -0.01644 0.02253 -0.01800 0.02956 -0.01953 0.03876 -0.02098 0.05086 -0.02220 0.06651 -0.02308 0.08566 -0.02362 0.10687 -0.02393 0.12869 -0.02401 0.15089 -0.02391 0.17339 -0.02368 0.19597 -0.02337 0.21855 -0.02297 0.24109 -0.02251 0.26357 -0.02200 0.28601 -0.02144 0.30841 -0.02085 0.33079 -0.02023 0.35315 -0.01959 0.37549 -0.01891 0.39782 -0.01821 0.42015 -0.01749 0.44247 -0.01673 0.46479 -0.01595 0.48711 -0.01513 0.50943 -0.01429 0.53175 -0.01342 0.55407 -0.01251 0.57639 -0.01157 0.59871 -0.01060 0.62103 -0.00962 0.64335 -0.00864 0.66567 -0.00767 0.68800 -0.00673 0.71036 -0.00582 0.73279 -0.00494 0.75530 -0.00407 0.77776 -0.00320 0.80018 -0.00229 0.82264 -0.00135 0.84494 -0.00044 0.86681 0.00040 0.88806 0.00108 0.90848 0.00151 0.92796 0.00161 0.94637 0.00129 0.96339 0.00052 0.97834 -0.00064 0.99047 -0.00204 0.99980 -0.00357 |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
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Polars for AH 94-145 (ah94145-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah94145-il | 50,000 | 9 | 6.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94145-il | 50,000 | 5 | 14.8 at α=13.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah94145-il | 100,000 | 9 | 28 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94145-il | 100,000 | 5 | 30.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah94145-il | 200,000 | 9 | 75.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94145-il | 200,000 | 5 | 81.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah94145-il | 500,000 | 9 | 135.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94145-il | 500,000 | 5 | 132.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah94145-il | 1,000,000 | 9 | 177.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94145-il | 1,000,000 | 5 | 164.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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